(19)
(11) EP 2 452 878 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
14.01.2015 Bulletin 2015/03

(43) Date of publication A2:
16.05.2012 Bulletin 2012/20

(21) Application number: 11250897.3

(22) Date of filing: 16.11.2011
(51) International Patent Classification (IPC): 
B64D 27/16(2006.01)
F02C 7/32(2006.01)
 B64D 41/00(2006.01)
F02C 7/36(2006.01)
(84) Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated Extension States:
BA ME

(30) Priority: 16.11.2010 US 947451

(71) Applicant: Rolls-Royce Corporation
Indianapolis, IN 46241 (US)

(72) Inventors:
  • Burns, Donald
    Avon, Indiana 46123 (US)
  • Rajashekara, Kaushik
    Carmel, Indiana 46032 (US)

(74) Representative: Roberts, Peter David et al
Marks & Clerk LLP 1 New York Street
Manchester, M1 4HD
Manchester, M1 4HD (GB)

   


(54) Aircraft, propulsion system, and system for taxiing an aircraft


(57) A propulsion system (18) for an aircraft, comprising:
a gas turbine engine having at least a high pressure (HP) spool (24) and a low pressure (LP) spool (26), wherein the LP spool (26) is operative to drive a propulsor (28); and
a hybrid auxiliary power unit (APU) (22) mechanically coupled to both the HP spool (24) and the LP spool (26), wherein the hybrid APU (22) includes an APU compressor (60); an APU turbine (64); and a fuel cell (62) fluidly disposed between the APU compressor (60) and the APU turbine (64), wherein the fuell cell (62) is operative to receive as an oxidant air pressurized by the APU compressor (60); to generate electrical power using a fuel and the oxidant; to heat the air pressurized by the APU compressor (60); and to discharge the heated pressurized air into the APU turbine (64), wherein the hybrid APU (22) is operative to supply rotational power to both the HP spool (24) and the LP spool (26).







Search report












Search report